CN114147994B - Integral forming method for composite cabin structure - Google Patents
Integral forming method for composite cabin structure Download PDFInfo
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- CN114147994B CN114147994B CN202111403569.9A CN202111403569A CN114147994B CN 114147994 B CN114147994 B CN 114147994B CN 202111403569 A CN202111403569 A CN 202111403569A CN 114147994 B CN114147994 B CN 114147994B
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- ring frame
- longitudinal force
- cabin
- composite material
- force transmission
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/80—General aspects of machine operations or constructions and parts thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses an integral forming method of a composite material cabin structure, which belongs to the technical field of composite material application and manufacturing, and the integral forming method is characterized in that the cabin structure is divided into a ring frame structure, a longitudinal force transmission structure and an integral skin structure by a structural process parting combined integral process forming mode, then the composite material is used for independent forming respectively, and then the composite material cabin structure is obtained by assembling, so that the forming quality and the forming precision of the composite structure cabin structure can be improved, the light weight level of the structure can be improved, and the integral forming of a large-size composite structure cabin can be realized.
Description
Technical Field
The invention belongs to the technical field of composite material application and manufacturing, and particularly relates to an integral forming method of a composite material structure.
Background
Compared with the traditional metal material, the carbon fiber composite material has the characteristics of high specific modulus, high specific strength and the like, and can furthest lighten the structural weight while meeting the structural performance requirement.
For a large-size composite material cabin structure, the traditional multi-wall plate forming process scheme has the defects of high fastener use quantity and insufficient light weight level; the integral molding by adopting the metal mold has the problems of different thermal expansion coefficients between the composite material product and the metal molding mold, large weight of the metal mold, inconvenient operation and the like, so that the integral molding of the large-size composite material cabin by adopting the mold has no process feasibility. At present, no mature solution exists for integrally forming the large-size composite material cabin, so how to integrally form the large-size composite material cabin becomes a technical problem to be solved urgently by relevant operators.
Disclosure of Invention
The invention aims at solving the problem that the integral molding of a large-size composite material cabin body by adopting a metal mold is not feasible, and provides an integral molding method of a composite material cabin body structure.
In order to achieve the above purpose, the invention adopts the following technical scheme:
the integral forming method of the composite cabin structure comprises the following steps:
1) Making a cabin structure parting scheme, dividing the cabin structure into a plurality of ring frame structures, a plurality of longitudinal force transmission structures and an integral skin structure, wherein the split surfaces between any two ring frame structures are axial matching surfaces, and the ring frame structures comprise a plurality of grooves along the axial direction of the cabin; the longitudinal direction of the longitudinal force transmission structure is along the axial direction of the cabin body and is assembled in the groove of the ring frame structure through the outer profile of the longitudinal force transmission structure;
2) The composite material is utilized, the annular frame structure which accords with the cabin structure parting scheme is independently formed through a forming process of an autoclave, a mould pressing or RTM, and the longitudinal force transmission structure which accords with the cabin structure parting scheme is independently formed through a forming mode of an expansion mould auxiliary mould pressing and a soft film;
3) After the ring frame structure and the longitudinal force transmission structure are respectively and independently molded, all the ring frame structures are aligned and bonded through axial matching surfaces of the ring frame structures through an autoclave or a hot oven, all the longitudinal force transmission structures are assembled and bonded in grooves of the ring frame structures through outer molded surfaces of the ring frame structures, the bonded whole is used as an outer skin molding tool, and the outer surface of the whole is used as a paving surface of an outer skin;
4) And (3) integrally paving the composite material outer skin on the paving surface of an outer skin forming tool, curing by an autoclave process, and packaging by a bag making mode to finally form the composite material cabin body structure.
Preferably, the composite material is selected from high-strength medium-mode carbon fibers, including T300, T700, T800 or T1100; or selecting high-strength high-modulus carbon fibers, including M40J or M55J.
Preferably, the resin system of the composite material is selected from medium-temperature epoxy, high-temperature epoxy, bismaleic resin, cyano resin or polyimide.
Preferably, the ring frame structure is a ring frame structure having web features, including a C-shaped ring frame structure.
Preferably, the cross section of the longitudinal force transfer structure is a closed cap structure or a closed loop structure.
Preferably, the axial matching surface of the ring frame structure is formed by a forming tool or machining, so that the profile degree of the matching surface is not more than 0.1mm.
Preferably, the axial matching surface of the ring frame structure reserves a space allowance for bonding of not more than 0.2 mm.
Preferably, the outer surface of the longitudinal force transfer structure is reserved with a space allowance for bonding of not more than 0.2 mm.
Preferably, the assembly process of the ring frame structure and the longitudinal force transmission structure is performed by using an assembly type frame with assembly precision smaller than 0.1mm, and the assembly type frame adopts a positioning and supporting structure to ensure the stability of the ring frame structure and the longitudinal force transmission structure in the bonding process.
Preferably, the bonding between the ring frame structures and the bonding between the longitudinal force transmission structure and the ring frame structures are all flexible adhesive films, and the flexible adhesive films are J-47, J-271 or J-188.
Preferably, the overall laying of the outer skin is carried out using a manual laying or an automatic wire laying machine.
The invention has the following advantages: the integral molding method of the composite material cabin structure provided by the invention has the advantages that the assembly between the ring frame structures and the longitudinal force transmission structure takes the molding surface as a reference, and the precision is high; the clearance space reserved on the axial matching surface of the ring frame structure and the assembly surfaces such as the outer molded surface of the longitudinal force transmission structure is compensated by the flexible adhesive film for subsequent bonding, so that smooth butt joint is realized. The invention can realize the integral molding of the large-size composite structure cabin body by adopting an innovative structural process parting mode and a process molding mode.
Drawings
Fig. 1 is a schematic view of the assembly positions of the ring frame structure and the longitudinal force transmission structure.
FIG. 2 is a schematic illustration of bonding of axial mating surfaces of a plurality of ring frame structures.
Fig. 3 is a schematic view of a single ring frame structure.
Fig. 4 is a schematic view of a single longitudinal force transfer structure.
Reference numerals illustrate:
10: a ring frame structure;
11: a groove;
12: an axial mating surface;
20: a longitudinal force transfer structure;
21: an outer profile.
Detailed Description
In order to make the above features and advantages of the present invention more comprehensible, embodiments accompanied with figures are described in detail below.
The embodiment discloses a method for integrally forming a composite cabin structure, which comprises the following steps:
1) Formulating a cabin structure parting scheme, wherein the scheme is as follows: the cabin structure is divided into a plurality of ring frame structures 10, a plurality of longitudinal force transfer structures 20 and a whole skin structure, wherein the ring frame structures 10 and the longitudinal force transfer structures 20 are shown in fig. 1, 3 and 4. The separated surfaces between any two ring frame structures 10 are axial matching surfaces 12, the ring frame structures 10 are C-shaped, and the ring frame structures 10 comprise a plurality of grooves 11 along the axial direction of the cabin. The longitudinal force transfer structure 20 is formed in the longitudinal direction of the cabin, and its cross section is formed as a closed cap structure, and in other embodiments may be formed as a closed ring structure, and is fitted into the groove 11 of the ring frame structure 10 by its outer surface 21.
2) A composite material is selected, which selects the high-strength medium-mode carbon fiber T300, and in other embodiments, other high-strength medium-mode carbon fibers T700, T800, or T1100, or high-strength high-mode carbon fibers M40J or M55J may be selected. The resin system selected for the composite material is medium temperature epoxy resin, and in other embodiments, high temperature epoxy, bismaleimide resin, cyano resin, polyimide, or the like can also be selected.
Then the ring frame structure 10 which accords with the cabin structure parting scheme is independently molded through an autoclave, a compression molding or RTM molding process, and the longitudinal force transmission structure 20 which accords with the cabin structure parting scheme is independently molded through an expansion mold auxiliary compression molding and a soft film molding mode. Wherein the axial matching surface 12 of the ring frame structure 10 is formed by a forming tool or machining, so that the profile degree of the matching surface 12 is not more than 0.1mm, and the axial matching surface 12 of the ring frame structure 10 is reserved with a space allowance for bonding not more than 0.2 mm. The outer profile 21 of the longitudinal force transfer structure 20 is reserved with a space margin for adhesion of not more than 0.2 mm.
3) After the ring frame structure 10 and the longitudinal force transmission structure 20 are respectively and independently formed, an assembly type frame with the assembly precision smaller than 0.1mm is adopted for assembly, and the assembly type frame adopts a positioning and supporting structure, so that the stability of the ring frame structure 10 and the longitudinal force transmission structure 20 in the assembly process can be ensured.
All ring frame structures 10 are aligned and bonded through the axial matching surfaces 12 of the ring frame structures through an autoclave or a hot oven, as shown in fig. 2, all longitudinal force transmission structures 20 are assembled and bonded in grooves 11 of the ring frame structures 10 through the outer molded surfaces 21 of the longitudinal force transmission structures, the bonded whole is used as an outer skin forming tool, and the outer surface of the whole is used as a paving surface of an outer skin. The flexible adhesive films J-47, J-271 or J-188 are adopted for bonding, and are not limited, and the flexible adhesive films exist in a space which is not more than 0.2mm and reserved by the axial matching surface 12 of the ring frame structure 10 and the outer surface 21 of the longitudinal force transmission structure 20.
4) After the ring frame structure 10 and the longitudinal force transmission structure 20 are assembled, the outer skin made of the same composite material is integrally paved on the paving surface of the outer skin forming tool through a manual paving process or an automatic wire paving machine paving process, is solidified through an autoclave process, is packaged through a bag making mode, and finally forms the composite material cabin structure.
The embodiment of the invention can realize the integral molding of the large-size composite structure cabin body by adopting an innovative structural process parting mode and a process molding mode, and can solve the problem that the integral molding of the large-size composite material cabin body by adopting a metal die is not feasible.
Although the present invention has been described with reference to the above embodiments, it should be understood that the invention is not limited thereto, and that modifications and equivalents may be made thereto by those skilled in the art, which modifications and equivalents are intended to be included within the scope of the present invention as defined by the appended claims.
Claims (10)
1. The integral forming method of the composite cabin structure is characterized by comprising the following steps of:
1) Making a cabin structure parting scheme, dividing the cabin structure into a plurality of ring frame structures, a plurality of longitudinal force transmission structures and an integral skin structure, wherein the split surfaces between any two ring frame structures are axial matching surfaces, and the ring frame structures comprise a plurality of grooves along the axial direction of the cabin; the longitudinal direction of the longitudinal force transmission structure is along the axial direction of the cabin body and is assembled in the groove of the ring frame structure through the outer profile of the longitudinal force transmission structure;
2) The composite material is utilized, the annular frame structure which accords with the cabin structure parting scheme is independently formed through a forming process of an autoclave, a mould pressing or RTM, and the longitudinal force transmission structure which accords with the cabin structure parting scheme is independently formed through a forming mode of an expansion mould auxiliary mould pressing and a soft film;
3) After the ring frame structure and the longitudinal force transmission structure are respectively and independently molded, all the ring frame structures are aligned and bonded through axial matching surfaces of the ring frame structures through an autoclave or a hot oven, all the longitudinal force transmission structures are assembled and bonded in grooves of the ring frame structures through outer molded surfaces of the ring frame structures, the bonded whole is used as an outer skin molding tool, and the outer surface of the whole is used as a paving surface of an outer skin;
4) And (3) integrally paving the composite material outer skin on the paving surface of an outer skin forming tool, curing by an autoclave process, and packaging by a bag making mode to finally form the composite material cabin body structure.
2. The method of claim 1, wherein the composite material is selected from the group consisting of high strength medium mode carbon fibers, including T300, T700, T800, and T1100; or selecting high-strength high-modulus carbon fibers including M40J or M55J; the resin system of the composite material is selected from medium-temperature epoxy, high-temperature epoxy, bismaleimide resin, cyano resin or polyimide.
3. The method of claim 1, wherein the ring frame structure is a web-feature ring frame structure, including a C-ring frame structure.
4. The method of claim 1, wherein the longitudinal force transfer structure has a cross-section that is a closed cap structure or a closed loop structure.
5. The method of claim 1, wherein the axial mating surface of the ring frame structure is contoured to no more than 0.1mm by a forming tool or machining.
6. The method of claim 1, wherein the axially facing surface of the ring frame structure reserves a bonding space margin of no more than 0.2 mm.
7. The method of claim 1, wherein the exterior surface of the longitudinal force transfer structure is reserved with a bonding space margin of no more than 0.2 mm.
8. The method of claim 1, wherein the ring frame structure and the longitudinal force transfer structure are assembled using an assembly jig having an assembly accuracy of less than 0.1mm.
9. The method of claim 1, wherein the bonding between the ring frame structures and the bonding between the longitudinal force transfer structure and the ring frame structures are each a flexible adhesive film selected from the group consisting of J-47, J-271 and J-188.
10. The method of claim 1, wherein the overall laying of the outer skin is performed using a manual laying or an automatic wire laying machine.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111403569.9A CN114147994B (en) | 2021-11-24 | 2021-11-24 | Integral forming method for composite cabin structure |
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| CN202111403569.9A CN114147994B (en) | 2021-11-24 | 2021-11-24 | Integral forming method for composite cabin structure |
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| CN114147994A CN114147994A (en) | 2022-03-08 |
| CN114147994B true CN114147994B (en) | 2023-05-05 |
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